Electrodynamic deorbiting of LEO satellites

In this paper we present realistic calculations of deorbiting times for a LEO satellite through the use of electrodynamic tethers. We refer to two possible tether systems (a bare and a conducting insulated tether) both equipped with an inflatable conducting balloon at the upper end. The calculations take into account average ionospheric properties and the electrical interaction of the wire with the ionosphere. Furthermore, they have been done for several inclination orbits and include also the deviation of the tether from the vertical direction under the combined action of the gravity gradient and the electrodynamic forces. The results obtained for the decay times, for typical constellation satellite, indicate that such tether systems are definitely of interest for the deorbiting application.